Apparatus and method for ordinance mounting system

ABSTRACT

Embodiments of a payload attachment system secure a payload to a wing or fuselage of the drone  102  (or another type of aircraft) using one or more vacuum mounting modules, wherein each vacuum mounting module comprises at least one vacuum pump controllably coupled to a microcontroller, a vacuum cup fluidly coupled to the at least one vacuum pump, and a transceiver that receives an instruction corresponding to one of a vacuum cup actuation signal or a vacuum cup release signal.

BACKGROUND OF THE INVENTION

In various situations, it is desirable to releasably secure ordinance,interchangeably referred to herein as a payload, to an aircraft,unmanned drone, or the like. Typically, such ordinance are suspendedfrom the fuselage and/or wings of the aircraft or the frame of a drone.Payloads are secured at a hard point that is structurally capable ofsupporting a predefined payload that weighs less than some predefinedmaximum weight. The payload is mateably secured to the aircraft or droneusing a connector on the distal end of a pylon. The payload may besecured directly to the pylon. Or, if multiple payloads are secured to apylon, the payloads may be secured to a rack that is secured to thedistal end of the pylon.

FIG. 1 is a front view diagram of an example legacy military purposedaerial drone 102. Here, the non-limiting example payload 104 is theAGM-114 (air to ground missile) Hellfire. With a weight of just over onehundred pounds, the AGM-114 Hellfire may be a suitable payload 104 for adrone 102 because of its relatively small size and light weight. Anothernon-limiting example of a payload 104 is a smaller drone that might beused for surveillance and/or for delivering ordinance. Such payloads 104are suspended from the wings or fuselage of the drone 102 using a pylon106.

The illustrated example drone 102 is propelled forward by an engine andpropellor 106. Some military purposed drones are jet propelled. One ormore VTOL (vertical takeoff and landing) motors and propellors may beused for field launching and landing of the drone 102. Alternatively,some legacy drones have landing gear for takeoff and landing on a flatsurface, such as an airfield, road, aircraft carrier, or the like.

One problem encountered in the arts is that the radar reflections from apylon 106 may be undesirable, particularly if the drone is stealthy.That is, a stealthy drone is designed with an exterior that minimallyreflects incident radar energy. However, the pylon 106 may itself be asource of undesirable radar reflections. Accordingly, in the arts ofstealth technologies, there is a need in the arts for improved methods,apparatus, and systems for reducing radar reflections from pylons 106used to secure ordinance to a drone.

Further, ordinance is typically secured to the pylon 106 while the drone102 at a base station, such as an airfield, aircraft carrier, etc. Inpractice, travelling from the base station to the battlefield, and thenreturning back to the base station after the ordinance has been releasedfrom the drone 102, takes some amount of time (based on velocity of thedrone 102 and distance between the base station and the battlefieldsite). Accordingly, in the arts of using a military purposed drone 102or other aircraft, there is a need in the arts for improved methods,apparatus, and systems for quickly rearming military purposed drone 102or other aircraft without the need to return to the base station.

Also, attaching ordinance to the pylons 106 of a drone or other aircraftis a time consuming effort for the ground crew. Accordingly, in the artsof releasably securing payloads 104 to a drone 102 or other aircraft,there is a need in the arts for improved methods, apparatus, and systemsfor quickly securing the payload 104 to the military purposed drone 102or other aircraft.

Additionally, the attaching means that are used to secure the payload104 to a pylon 106 (or rack) may be limiting in that both the pylon 106(or rack) and the payload 104 must have corresponding connectors. If theconnectors on the pylon 106 do not match the connector on the payload104, the payload 104 cannot be secured to the pylon 106. Accordingly, inthe arts of releasably securing payloads 104 to a drone 102 or otheraircraft, there is a need in the arts for improved methods, apparatus,and systems for securing the payloads 104 when the connectors on thepylon 106 and payload 104 do not correspond, or to secure the payload104 with no connectors at all.

SUMMARY OF THE INVENTION

Embodiments of a payload attachment system secure a payload to a wing orfuselage of the drone 102 (or another type of aircraft) using one ormore vacuum mounting modules, wherein each vacuum mounting modulecomprises at least one vacuum pump controllably coupled to amicrocontroller, a vacuum cup fluidly coupled to the at least one vacuumpump, and a transceiver that receives an instruction corresponding toone of a vacuum cup actuation signal or a vacuum cup release signal.

BRIEF DESCRIPTION OF THE DRAWINGS

The components in the drawings are not necessarily to scale relative toeach other. Like reference numerals designate corresponding partsthroughout the several views.

FIG. 1 is a front view of a legacy military purposed aerial drone withordinance secured to a legacy pylon.

FIG. 2 is a front view of the legacy military purposed aerial drone withmissiles secured to the drone using an ordinance attachment system.

FIG. 3 is a front view of the legacy military purposed aerial drone witha plurality of small drones secured to the drone using an ordinanceattachment system.

FIG. 4 is a side cut away view of the vacuum mounting module with anon-limiting example cover member.

FIG. 5 is a side view of a missile with four vacuum mounting modules,wherein the vacuum control unit is secured to the outer surface of themissile using a suitable releasable connector.

FIG. 6 is a side view of a missile with four vacuum mounting modules,wherein the vacuum mounting modules each have two opposing vacuum cupssecured to the outer surface of the missile and to the wing or fuselageof the drone (or another type of aircraft).

FIG. 7 is a side view of a missile with four vacuum mounting modules,wherein the vacuum control unit is secured to a wing or fuselage of adrone (or another type of aircraft).

FIG. 8 is a side view diagram of an embodiment of a vacuum mountingmodule showing selected example electronic components.

FIG. 9 is a side cut away view of the vacuum mounting module with anon-limiting example cover member.

FIG. 10 is a side cut away view of the vacuum mounting module with twoopposing vacuum cups.

FIG. 11 is a block diagram of a vacuum mounting module control systememploying a designated vacuum control device that controls a pluralityof vacuum mounting modules.

FIG. 12 is a block diagram of a vacuum mounting module control systememploying mesh network wherein a plurality of vacuum mounting modulescooperatively control operation of the payload attachment system.

DETAILED DESCRIPTION

FIG. 2 is a front view of the legacy military purposed aerial drone 102with a plurality of missiles 104 a secured to the drone using anordinance attachment system 200. FIG. 3 is a front view of the legacyaerial drone 102 with a plurality of small drones 104 b secured to thedrone using an ordinance attachment system 200. As defined herein, theterm payload 104 refers to any payload of interest, such as thenon-limiting example missiles 104 a, the small drones 104 b, and/orother ordinance. The payload 104 is releasably secured to the drone 102(or another type of aircraft) using one or more vacuum mounting modules202.

FIG. 4 is a diagram of four vacuum mounting modules 202. Each vacuummounting module 202 includes a vacuum cup 204 and a vacuum control unit206. The vacuum cup 204 is disposed on an exterior of the vacuummounting module 202. The outside surface of the vacuum control unit 206(opposing the vacuum cup 204) is configured to be permanently securedto, or semipermanently secured to, a surface of a first object asdescribed hereinbelow.

When a vacuum within the interior of the vacuum cup 204 is created bythe vacuum control unit 206, the vacuum mounting module 202 becomesreleasably secured to the surface of a second object. In practice, inresponse to receiving a vacuum cup actuation signal from a vacuumcontrol device 208, the vacuum control unit 206 operates one or moreinternal vacuum pumps to create a vacuum having at least a predefinedvacuum level (a negative atmospheric pressure) within the interiorregion of the vacuum cup 204.

The vacuum cup actuation signal may be generated by a variety of vacuumcontrol devices 208 depending upon the particular embodiment of thepayload attachment system 100. For example, a payload installer mayprovide input to the vacuum control device 208 to establish a vacuum.Here, the payload installer would pair their vacuum control device 208with a plurality of vacuum control units 206 that are to be used for asecuring a particular payload 104.

For example, the payload 104 may be releasably secured the wing orfuselage of a drone 102 (or another type of aircraft). When the payload104 is held in place by one or more payload installers, the vacuum pumpsare actuated. The vacuum in each vacuum cup 204 then secures the payload104 to the drone 102 (or another type of aircraft). During flight to abattlefield, the secured payload 104 remains in place. In response to avacuum cup release signal, the vacuum in the vacuum cups 204 isreleased. The payload 104 then falls away from the drone 102 (or anothertype of aircraft).

In the various embodiments, pylons 106 are not needed to releasablysecure payloads to the drone 102 (or another type of aircraft). Anunexpected benefit provided by embodiments of the payload attachmentsystem 100 is that the undesirable radar reflections from the pylons 106are eliminated. Another unexpected benefit is that eliminating theweight of the pylons 106 may increase the total payload capacity of thedrone 102 (or another type of aircraft). Also, connectors on the payload104 and the pylon 106 are no longer required. Accordingly, the problemof unmatched connectors is removed.

Yet another advantage provided by embodiments of the payload attachmentsystem 100 is that the time required to secure a payload 104 to a drone102 (or another type of aircraft) is significantly reduced. And, thepayload installers do not have to use specialty designed tools. Rather,the payload installers simply hold the payload 104 in place until thevacuum in the vacuum cups 204 are established.

When the drone 102 (or another type of aircraft) has VTOL capabilities,the drone 102 (or another type of aircraft) can make multiple deliverieswhile in the field. For example, if a VTOL drone 102 is being used todeliver a plurality of AGM-114 Hellfire missiles 104 a (which only weigh104 lbs. each) in a battlefield, the VTOL drone 102 may deliver a firstplurality of missiles 104 a to targets of interest. Then, the VTOL drone102 may return back to a safe location behind friendly lines (ratherthan the remotely located base station). The VTOL drone 102 may then bequickly reprovisioned with a second plurality of missiles 104 a, andthen return to the battlefield.

The disclosed systems and methods for securing a payload 102 using thepayload attachment system 100 will become better understood throughreview of the following detailed description in conjunction with thefigures. The detailed description and figures provide examples of thevarious inventions described herein. Those skilled in the art willunderstand that the disclosed examples may be varied, modified, andaltered without departing from the scope of the inventions describedherein. Many variations are contemplated for different applications anddesign considerations, however, for the sake of brevity, each and everycontemplated variation is not individually described in the followingdetailed description.

Throughout the following detailed description, a variety of examples forsystems and methods for releasably securing a payload to a secured-toobject using the payload attachment system 100 are provided. Relatedfeatures in the examples may be identical, similar, or dissimilar indifferent examples. For the sake of brevity, related features will notbe redundantly explained in each example. Instead, the use of relatedfeature names will cue the reader that the feature with a relatedfeature name may be similar to the related feature in an exampleexplained previously. Features specific to a given example will bedescribed in that particular example. The reader should understand thata given feature need not be the same or similar to the specificportrayal of a related feature in any given figure or example.

The following definitions apply herein, unless otherwise indicated.

“Substantially” means to be more-or-less conforming to the particulardimension, range, shape, concept, or other aspect modified by the term,such that a feature or component need not conform exactly. For example,a “substantially cylindrical” object means that the object resembles acylinder, but may have one or more deviations from a true cylinder.

“Comprising,” “including,” and “having” (and conjugations thereof) areused interchangeably to mean including but not necessarily limited to,and are open-ended terms not intended to exclude additional, elements ormethod steps not expressly recited.

Terms such as “first”, “second”, and “third” are used to distinguish oridentify various members of a group, or the like, and are not intendedto denote a serial, chronological, or numerical limitation.

“Coupled” means connected, either permanently or releasably, whetherdirectly or indirectly through intervening components. “Secured to”means directly connected without intervening components.

“Communicatively coupled” means that an electronic device iscommunicatively connected to another electronic device, eitherwirelessly or with a wire based connector, whether directly orindirectly through a communication network. “Controllably coupled” meansthat an electronic device controls operation of another electronicdevice.

Returning to FIG. 4 , in preferred embodiments the vacuum control device208 may reside within the drone 102. The drone operator and/or thepayload installer can communicatively couple their electronic devices tothe vacuum control device 208 to cause generation of the actuationsignal or release signal.

To pair a vacuum control unit 206 with a vacuum control device 208, thepayload installer can simply turn on the plurality of vacuum mountingmodules 202 that are to be used to secure a payload 104. Other vacuummounting modules 202 that remain off will not respond to the vacuumcontrol device 208. Other embodiments may use any suitable pairingmethod.

Once the vacuum control device 208 is paired with the vacuum mountingmodules 202 and the payload is secured, drone 102 can travel to thebattlefield. Then, the vacuum control device 208 can receive releaseinstructions from the drone operator who is operating an electronicdevice that controls the drone 102 and the vacuum control device 208.

Since each vacuum mounting module 202 independently maintains a targetvacuum level within its respective vacuum cup 204, the payload 102 maybe secured for any period of time of interest. That is, the vacuumcontrol unit 206 may actuate an internal vacuum pump as needed tomaintain the predefined vacuum pressure between the surface and thevacuum cup 204. When the vacuum is released by the vacuum control unit206, the vacuum cup 204 releases from the object.

An optional outer seal 210 may be used to form a seal between thesurfaces of a wing or fuselage of the drone 102 (or other aircraft) anda payload 104. The outer seal 210 is a suitable semi-rigid or flexiblecompressible material that generally conforms to the shape and size ofthe outer perimeter of the one or more vacuum mounting modules 202. In apreferred embodiment, the outer seal 210 is made of neoprene, rubber,rubberized foam, or the like of a suitable thickness (height) that issufficient to create a cavity between the surfaces of the two objectsbeing secured together.

In the various embodiments employing the optional outer seal 210, inresponse to actuation of the payload attachment system 100, air is drawnout from the plurality of vacuum mounting modules 202. The flexiblevacuum cups 204 partially collapse, decreasing their height as thevacuum within the vacuum cups 204 is created. The downward collapse ofthe vacuum cups 204 pulls the surfaces of a wing or fuselage of thedrone 102 (or other aircraft) and the payload 104 together. Accordingly,the outer seal 210 is compressed to form a frictional seal between thesurfaces of the wing or fuselage of the drone 102 (or other aircraft)and the payload 104. Since the vacuum cups 204 are within the cavityformed by the compressed outer seal 210, the vacuum cups 204 areprotected from weather and/or forces created by moving air. That is,since the outer seal 210 is made of a flexible and air tight materialsuch as neoprene or the like, the outer seal 210 serves to diffuseweather and moving air away from the vacuum cups 204 to avoiddisturbance to the vacuum cups 204. By protecting the seal of the vacuumcups 204, power requirements on the vacuum pumps may be decreased.Further, reliability may be increased to the leading edge vacuum cups204 that may otherwise experience the greatest “lift” during movement ofthe drone 102.

In some embodiments, the outer seal 210 is affixed to the payload 102 orthe surface the wing or fuselage of the drone 102 (or another type ofaircraft) using a suitable means. The payload installer simply has tohold the payload 104 in place, preferably pushing the payload 104 gentlyonto the outer seal 210. When the vacuum is established, the payloadinstaller may release the payload 104 since the payload 104 is nowsecured to the wing or fuselage drone 102. The outer seal 210 may beaffixed to the surface using a suitable adhesive, a ferromagnetic orelectromagnetic strip, a ferromagnetic or electromagnetic materialdisposed within the outer seal 210, screws, bolts, loop and hookmaterial, etc.

An advantage of securing the outer seal 210 to the wing or fuselage of adrone 102 (or another type of aircraft) is that a variety of differentpayloads 104 can be secured so long as a portion of the surface of thepayload 104 is compatible with the outer seal 210 that is affixed to thedrone 102 (or another type of aircraft). An advantage of affixing theouter seal 210 to the payload 104 is that a variety of differentpayloads 104 may be secured to the drone 102 (or another type ofaircraft) at any location on the wing or the fuselage.

An advantage of using ferromagnetic or electromagnetic materials tosecure the outer seal 210 is that different outer seals 210 may beselectively used depending upon the characteristics of the payload 104and/or the drone 102 (or another type of aircraft). Further, if amagnetically secured outer seal 210 is damaged, the damaged outer seal210 can be easily replaced in the field by a payload installer.

In some embodiments, the outer seal 210 is not secured to either of thesurfaces of the drone 102 (or another type of aircraft) and the payload104. In such embodiments, the payload 104 and the outer seal 210 areplaced in position and are secured by the vacuum mounting modules 202.When the payload 104 is released, the outer seal 210 is sacrificed andsimply falls to the ground.

In some instances, the outer seal 210 may be initially provided as asheet of material that the payload installer may cut to a desired shapeand size. The embodiment may be particularly advantageous when differenttypes of payloads 104 are being releasably secured to the drone 102 (atthe same time, or at different times). Alternatively, or additionally, apre-cut outer seal 210 may be provided that is cut based on thedimensions of the payload 104.

FIG. 5 is a side view of a missile 104 a with four vacuum mountingmodules 204, wherein the vacuum control unit 206 is secured to the outersurface of the missile 104 a using a suitable releasable connector. Whenthe missile 104 a is fired by the operator of the drone 102 (or anothertype of aircraft) by releasing connectors between the surface of themissile 204 a and the vacuum mounting module 202, the vacuum mountingmodules 202 remain releasably secured to the drone 102. When the drone102 returns to its home base, the vacuum mounting modules 202 can bereleased to clear the wings and/or fuselage of the drone 102. Thosereleased vacuum mounting modules 202 can be used at a later time onanother missile 104 a. After the vacuum mounting modules 202 arereleased, the payload installer may then install a new similarly fittedmissile 104 a. The drone 102 may return to the battlefield. Embodimentsof the payload attachment system 100 may enable rearming of a drone 102in a very short time, even rearming the drone 102 in a matter of a fewminutes. And, if the drone 102 (or other aircraft) has VTOLcapabilities, the drone 102 (or other aircraft) does not need to returnto the remotely located home base.

FIG. 6 is a side view of a missile 104 a with four vacuum mountingmodules 204, wherein the vacuum mounting modules 202 each have twoopposing vacuum cups 204 secured to the outer surface of the missile 104a and to the wing or fuselage of the drone 102 (or another type ofaircraft). Here, during installation, the vacuum cups 204 may beinitially secured to the missile 104 a. Then, the payload installerholds the missile 104 a in place on the wing or fuselage of the drone102. Once a vacuum is established in the opposing vacuum cups 204, themissile 104 a is then releasably secured to the drone 102. The processmay first secure the vacuum mounting modules 202 to the missile 104 a,and then secure the vacuum mounting modules 202 to the surfaces of thewing or fuselage of the drone 102 (or other aircraft).

When the missile 104 a is fired by the operator of the drone 102 (oranother type of aircraft), the vacuum mounting modules 202 remainreleasably secured to the drone 102. When the drone 102 returns to itshome base, the vacuum mounting modules 202 can be released to clear thewings and/or fuselage of the drone 102. Those released vacuum mountingmodules 202 can be used at a later time on another missile 104 a. Afterthe vacuum mounting modules 202 are released, the payload installer maythen install a similarly fitted missile 104 a.

Alternatively, the payload installer may simple secure a new payload 104to the previously installed vacuum mounting modules 202 that are on thesurfaces of the wing or fuselage of the drone 102 (or other aircraft).However, completely removing a previously used vacuum mounting module202 may increase reliability since the removed vacuum mounting module202 can be inspected for damage before reuse.

After the new payloads 104 are installed, the drone 102 may return tothe battle field. Embodiments of the payload attachment system 100 mayenable rearming of a drone 102 in a very short time, even rearming thedrone 102 in a matter of a few minutes. Further, the payload installersmay secure the released vacuum mounting modules 202 to the other missile104 a while the drone 102 is returning to and from the battlefield.

If the drone 102 (or other aircraft) has VTOL capabilities, the drone102 (or other aircraft) does not need to return to the remotely locatedhome base. Rather, the drone 102 may return to a safe location away fromthe battlefield, and then be quickly rearmed for return to thebattlefield.

FIG. 7 is a side view of a missile 104 a with four vacuum mountingmodules 202, wherein the vacuum control unit is secured to a wing orfuselage of a drone 102 (or another type of aircraft). Here, duringinstallation, the payload installer holds the missile 104 a in place onthe vacuum cups 204 that are on the wing or fuselage of the drone 102.Once a vacuum is established in the vacuum cups 204, the missile 104 ais then releasably secured to the drone 102. Like the embodimentsillustrated in FIGS. 5 and 6 , the example embodiment of FIG. 7 enablesrearming of a drone 102 in a very short period of time.

In some embodiments, the vacuum cup 204 is releasably secured to avacuum mounting module 202. Here, if the vacuum cup 204 is damagedduring use, the payload installer may easily replace the damaged vacuumcup 204. Alternatively, or additionally, different vacuum cups 204 maybe suitable for different types of payloads 104. Here, the payloadinstaller may used the most appropriate vacuum cup 204 for the currentpayload 104 that is being installed.

FIG. 8 is a side view diagram of an embodiment of a vacuum mountingmodule 202 showing selected example electronic components. Thenon-limiting exemplary vacuum mounting module 202 comprises a powersupply 802, a vacuum pump 804 (with an optional venturi and a checkvalve), a pressure sensor 806, one or more optional environmentalsensors 808, a transceiver 810, an optional user interface 812, optionalindicator lights 814, a processor system 816 (interchangeably referredto herein as a microcontroller), and a memory 818. The memory 818comprises portions for storing the transceiver module 820, the userinterface module 822, the vacuum pump and check valve module 824, andthe monitoring module 826. In some embodiments, transceiver module 820,the user interface module 822, the vacuum pump module and check valve824, and the monitoring module 826 may be integrated together, and/ormay be integrated with other logic. In other embodiments, some or all ofthese memory and other data manipulation functions may be provided byusing a remote server or other electronic devices suitably connected viathe Internet or otherwise to a client device. Other embodiments of avacuum mounting module 202 may include some, or may omit some, of theabove-described components. Further, additional components not describedherein may be included in alternative embodiments.

The power supply 802 is preferably a battery-based power supply thatpowers the processor system 816, the vacuum pump 804 (and the optionalventuri and the check valve), and other selected components. Replaceablebatteries and/or rechargeable batteries may be used. Preferably, thepower available from the power supply is sufficient to operate thevacuum mounting module 202 for at least a predefined semi-permanentduration, which may be several weeks, several months, or even a year ormore. Any suitable power source may be used in alternative embodiments,such as, but not limited to, a generator or other power source in thedrone 102, solar power, magnetic power, etc.

In a preferred embodiment, the processor system 816 monitors the powerthat is currently available from the power supply 802. If the powerdecreases below a threshold, a warning notification may be communicatedfrom the processor system 816 to the vacuum control device 208 and/or tothe drone operator's remote control system. In some embodiments, powermanagement recommendation may be made to the drone operator and/or thepayload installer so that they can manage use of the vacuum mountingmodules 202. For example, if the power is supplied by batteries and if alow battery condition occurs, or if a low battery condition can beprojected to occur in the near future, the drone operator and/or thepayload installer may be notified of remaining power or battery life.Then, the drone operator and/or the payload installer may choose toreplace one or more of the batteries of the power supply 802, and/orrecharge the batteries if the batteries are rechargeable.

The vacuum pump 804, which is controllably coupled to the processorsystem 816, is an electric vacuum pump that establishes a vacuum(pressure that is less than the actual air pressure) that is sufficientto secure the vacuum cup 204 to a surface of the surfaces of the wing orfuselage of the drone 102 (or other aircraft) and/or the payload 104.

An optional venturi may be used with the vacuum pump 804. The venturivalve may be a mechanical valve that uses a spring or the like tooperate the valve, or may be an active venturi valve that useselectricity to operate the valve. The pressure differential across theventuri, if used, enhances the efficiency of the vacuum pump 804.

The processor system 816, executing the vacuum pump and check valvemodule 824, controls operation of the vacuum pump 804. In response toreceiving a vacuum cup actuation signal, the vacuum pump 804 is operatedto create the vacuum that releasably secures vacuum mounting module 202to the surfaces of the wing or fuselage of the drone 102 (or otheraircraft) and/or the payload 104. The processor system 816, in responseto receiving a vacuum cup release signal, operates the vacuum pump 804to release the vacuum to release the surfaces of the wing or fuselage ofthe drone 102 (or other aircraft) and/or the payload 104 from the vacuummounting module 202. Any suitable vacuum pump 202 now known or laterdeveloped is intended to be included within the scope of this disclosureand to be protected by the accompanying claims.

Multiple vacuum pumps 804 provide reliability in the event of a singlevacuum pump 804 failure. Any desired number of vacuum pumps 804 may beused in the various embodiments. Also, multiple vacuum pumps 804 can beused to cooperatively create a stronger vacuum. A preferred embodimenthas two vacuum pumps 804 a, 804 b. In a preferred embodiment, the secondpump 804 b may be a piezoelectric pump or other suitable micro pump.Piezoelectric pumps may be used to maintain vacuum pressure while thedrone 102 (or another type of aircraft) is operating in a stealth modesince a piezoelectric pump is very quiet during operation.

Alternatively, or additionally, the vacuum cup 204 may include a smalldepressurized canister or bottle, or a microchamber, as a source ofnegative air pressure that can be quickly applied inside of the vacuumcup 204. Alternatively, the depressurized canister or bottle may residewithin the payload 104 (see FIG. 5 , for example) and/or within thedrone 102 or other type of aircraft (see FIG. 7 , for example).

An optional pressure sensor 806 monitors pressure within the vacuum cup204. In an example embodiment, a pressure sensor 806 is located withinthe vacuum mounting module 202 to sense vacuum pressure. The pressuresensor 806 may be a separate component located within the interior ofthe vacuum cup 204 or at a vacuum port 408 (FIG. 4 ) of the vacuumpump(s) 204. Alternatively, or additionally, the pressure sensor 806 maybe an integrated component of the vacuum pump 804.

The pressure sensor 806 is communicatively coupled to the processorsystem 816 (interchangeably referred to herein as a microcontroller).The microcontroller 816, executing the monitoring module 826, monitorsthe sensed vacuum pressure within the vacuum cup 204 on a real timebasis. Once a vacuum has been established to releasably secure thepayload to the vacuum cup 204, the processor system 816, executing thevacuum pump module and check valve 824, may further operate the vacuumpump 804 in response to the monitored pressure within the vacuum cup 204dropping below some predefined threshold. Accordingly, the vacuumpressure within each of the plurality of vacuum cups 204 can becontrolled to any desired predetermined pressure value or range.

For example, the vacuum within the plurality of vacuum cups 204 willvary with elevation. In instances where the drone 102 to a relativelyhigher elevation, or returns down to a lower elevation, the processorsystem 816 may operate the vacuum pump(s) 204 to adjust and/or maintainthe vacuum pressure to the desired target pressure value or range as theelevation changes. For example, the sensor 806 may sense current vacuumpressure. The processor system 816 compares the current vacuum pressureto one of more predefined thresholds. Instructions are communicated tothe vacuum pump(s) 804 to increase or decrease the vacuum pressure.Accordingly, a change in vacuum pressure is performed so that thecurrent vacuum pressure remains as some predefined value (or range).

As another example, the vacuum pressure may be varied as a function ofdrone velocity. Here, a higher vacuum pressure may be generated athigher drone velocities to ensure that the vacuum mounting modules 202do not become disengaged from the drone 102 and/or the payload 104 dueto the increasing wind created by the increased velocity of the drone102. A velocity sensor (not shown), such as a speedometer, providescurrent speed information to the processor system 816. The processorsystem 816 compares the current vacuum pressure to predefined vacuumpressures associated with speed. Instructions are communicated to thevacuum pump(s) 804 to increase or decrease the vacuum pressure to a newvacuum pressure that corresponds to the current velocity. Accordingly, achange in vacuum pressure is performed so that the current vacuumpressure value (or range) is appropriate for the current velocity.

In the various embodiments, a predefined vacuum pressure or pressurerange may be maintained within the vacuum cup 204. For example, a slowleak between the edges of the vacuum cup 204 and the surface of thereleasably secured payload may result in a loss of vacuum pressure. Thesensor 806 may sense current vacuum pressure that is decreasing due tothe slow leak. The processor system 816 compares the current vacuumpressure to one of more predefined thresholds. Instructions arecommunicated to the vacuum pump(s) 204 to increase or decrease thevacuum pressure. Accordingly, a change in vacuum pressure is performedso that the current vacuum pressure remains as some predefined value (orrange). Accordingly, the vacuum control unit 206 may automaticallyoperate once the vacuum pressure has fallen outside of the predefinedthreshold or threshold range to re-establish the vacuum pressure.

As another example, changing environmental conditions, such astemperature and/or altitude, may be changing the vacuum pressure,thereby causing the control unit 206 to automatically operate inresponse to the vacuum pressure falling or increasing beyond apredefined threshold or threshold range to re-establish the vacuumpressure. Here, the sensor 806 may sense current vacuum pressure that ischanging due to changing environmental conditions. The processor system816 compares the current vacuum pressure to one of more predefinedthresholds. Instructions are communicated to the vacuum pump(s) 804 toincrease or decrease the vacuum pressure. Accordingly, a change invacuum pressure is performed so that the current vacuum pressure remainsas some predefined value (or range).

The environmental sensors 808 may be used to monitor externalenvironmental conditions, such as humidity, rain, wind speed, ambientair pressure, temperature or the like. Based on sensed environmentalconditions, the processor system 816, executing the vacuum pump moduleand check valve 824, may modify the predefined minimum vacuum pressureso that the vacuum pressure maintained within the vacuum cup 204 issuitable for changing environmental conditions. For example, if altitudeincreases such that the ambient air pressure decreases, or the altitudedecreases such that ambient air pressure increases, then actual vacuumpressure may be automatically adjusted by the vacuum control unit 206and/or the vacuum control device 208 to maintain a predefined minimumand/or maximum vacuum pressure within the vacuum cup 204 or the vacuummounting modules 202. Alternatively, some embodiment may maintain apredefined pressure difference between the vacuum within the vacuum cup204 and the current ambient air pressure.

The transceiver 810 is configured to wirelessly receive and/or transmitwireless radio frequency (RF) communication signals to othertransceivers 810 residing in other vacuum mounting modules 202 and/orthe drone 102. In such embodiments, the wireless communicationtransceiver 810 may be a low power communication system, such as anear-field communication system. An example near-field communication isBluetooth. Any suitable low power and/or near-field communication systemnow known or later developed may be used in the various embodiments. Alow power near-field communication system is suitable because of theclose proximity of the vacuum mounting modules 202 and/or the dronetransceiver to each other.

Alternatively, or additionally, other wireless based communicationnetworks and/or hybrid communication networks may be communicativelycoupled to the transceiver 810. Example communication system include,but are not limited to, a cellular phone system, a Wi-Fi system, asatellite system, a radio frequency (RF) system, and/or a telephonysystem. In such embodiments, the transceiver 810 may be communicativelycoupled to the wireless communication system. Accordingly, thetransceiver 810 enables communication between a remote electronicdevice, such as the drone operator's remote control system, and thevacuum mounting modules 202. In some applications, the transceiver 810is communicatively coupled to the operator's portable hand heldelectronic device, such as a smart phone, notebook, or the like. In suchembodiments, the operator, while in the battlefield, may use theirportable hand held electronic device and/or another control system tooperate (initiate a vacuum cup release signal) and/or monitorperformance of the vacuum mounting modules 202.

In an example embodiment, the processor system 816, executing thetransceiver module 820, receives communications from and/or transmitscommunications to other vacuum mounting modules 202, the dronetransceiver, or another remote electronic device. As disclosed herein,the vacuum mounting module 202 operates the vacuum pump 804 to establisha vacuum within the vacuum cup 204 in response to the transceiver 810receiving the vacuum cup actuation signal from the one of the othervacuum mounting modules 202, the drone transceiver, and/or anotherremote electronic device. Conversely, the processor system 816,executing the transceiver module 820, may deactivate the vacuum pump 804to end the vacuum within the vacuum cup 204 in response to thetransceiver 810 receiving a vacuum cup release signal from the from oneof the other vacuum mounting modules 202, the drone transceiver, and/orfrom another remote electronic device such as the operator's droneremote control system.

An optional user interface 812 may be provided to enable manual controlof a vacuum mounting module 202 by a payload installer. A button, switchor other controller may enable the payload installer to manually actuatethe vacuum control unit 206. The processor system 816, executing theuser interface module 822, may operate the vacuum pump 804 to establisha vacuum within the vacuum cup 204 and/or to release the vacuum based oncontrol signals generated by the user interface 812 in response to thepayload installer's manual manipulation of the user interface 812.

For example, the payload installer may wish to relocate and/or reorientthe secured payload 104 after the payload 104 has been initially securedto the drone 102 (or another type of aircraft). For instance, locationand/or orientation of a missile 104 a that has been secured to a surfacethe wing or fuselage of the drone 102 may be changed to adjust theorientation of the missile 104 a. The payload installer may manuallydeactivate one or more of the vacuum mounting modules 202 to implementthe adjustment, and then reactivate those vacuum mounting modules 202 toreestablish the vacuum within the vacuum cups 204.

One or more optional indicator lights 814 may be provided on theexterior of the vacuum mounting module 202 and/or the vacuum controldevice 208 to indicate operational status of the device and/or system.For example, the processor system 816 may cause the indicator light 814to emit light when the vacuum mounting module 202 is functioningproperly. Alternatively, or additionally, another colored light and/oranother indicator light may emit light when the vacuum mounting module202 is not properly working. Accordingly, the payload installer mayvisually discern whether a vacuum mounting module 202 is properlyoperating based on the visible output of an indicator light 814. Is someembodiments, the indicator light 814 may be remotely located. Here, theindicator light 814 would be communicatively coupled to another remotetransceiver. A light control signal, generated by the processor system816, would be communicated from the transceiver 810 to the othertransceiver. The light control signal would then be received by theremote indicator light 814.

FIG. 9 is a side cut away view of the vacuum mounting module 202 with anon-limiting example cover member 902. The vacuum control unit 206 ispreferably defined by a rigid or semi-rigid body member 904 (such as,but not limited to, a monocoque body) that defines a cavity that encasesthe various components within the vacuum control unit 206. Someembodiments may be formed as a monocoque body. The body member 904protects the various components within the body cavity from damage. In anon-limiting example embodiment, the monocoque body member 904 defines amonocoque cavity that secures and protects the components of the vacuumcontrol unit 206, and wherein the vacuum cup 204 is coupled to themonocoque body member 904.

The vacuum cup 204 is preferably made of a flexible or semiflexiblematerial that is air impermeable. In the various embodiments, the vacuumcup 204 is permanently secured to the body member 904 in an air tightfashion. In some embodiments, the body member 904 and the vacuum cup 204are formed as a unibody piece.

A port 906 fluidly couples the vacuum pumps 204 a, 204 b with theinterior cavity of the vacuum cup 204. A check valve 908 may be used tomaintain an established vacuum pressure within the interior of thevacuum cup 204. The check valve 908 has a cracking pressurecorresponding to the predefined vacuum pressure in the vacuum chambersuch that the predefined vacuum pressure is maintained within the vacuumcup 204 when the vacuum cup mounting system 100 is secured to thesurface of the object of interest. The check valve 908 may be amechanical check valve that uses a spring or the like to operate thevalve, or may be an active check valve that uses electricity to operatethe valve 908.

The example embodiment illustrated in FIG. 9 includes one or moreoptional manual disengagement tabs 910. The manual disengagement tab 910is an outward protruding member on the outer side of the vacuum cup 204.The tab 910 can be grasped by the user to lift a bottom portion of theflexible vacuum cup 204 away from the surface of the payload after thevacuum has been released. When the user grasps and pulls on the manualdisengagement tab 910, ambient air inrushes into the interior of thevacuum cup 204 so that any remaining vacuum pressure is released,thereby releasing the vacuum mounting module 202 from the payload. Anydesired number of manual disengagement tabs 910 may be provided at anylocation of interest in the various embodiments.

A plurality of apertures 912 (holes) are illustrated as being fabricatedinto the body member 904 of the vacuum control unit 206. These apertures912 are used to secure the cover member 902 to the upper surface of thebody member 904. The apertures 912 may be threaded holes that matinglyreceive threaded bolts or screws 918 (FIG. 4 ) passing throughcorresponding apertures 912 in the cover member 902. When the bolts orscrews 918 are screwed into place and then tightened, the cover member902 becomes secured to the top of the body member 904. Alternatively,the apertures 912 may not be threaded such that a nut and bolt 918 maybe used to secure the cover member 902 to the body member 904 of thevacuum control unit 206. Alternatively, or additionally, other fasteningmeans such as threads, clamps, magnets, adhesive, or the like may beused to secure the cover member 902 to the top of the vacuum cup 204. Insome embodiments, the cover member 902 may be secured to, or made partof, the body member 904 of the vacuum control unit 206 duringfabrication.

The non-limiting example cover member 902 may include an optionaloutwardly protruding member 914 that protrudes outwardly from an outersurface of the cover member 902. Optional apertures 916 may be disposedthrough the outwardly protruding member 912. Bolts or screws 918 areused to secure the cover member 902 to the secured-to object. The heightof the outwardly protruding member 914, is this non-limiting exampleembodiment, is sufficiently high to permit access to the apertures 912when the bolts or screws 918 are used to secure the cover member 902 tothe top of the vacuum control unit 206.

Alternatively, the exterior edges of the cover member 902 may bethreaded. The interior surface near the top of the body member 904 mayhave mating threads. Once the cover member 902 is secured to thesurfaces of the wing or fuselage of the drone 102 (or other aircraft)and/or the payload 104, the body member 904 may be screwed onto thesecured cover member 902.

Alternatively, tabs or other protrusions (not shown) may extendoutwardly from the body member 904 and/or the cover member 902. Screws918, bolts 918 or the like can then be used to secure the vacuummounting module 202 to the surfaces of the wing or fuselage of the drone102 (or other aircraft) and/or the payload 104. Clips, snaps, rails, orthe like may be used to secure the vacuum mounting module 202 to thesurfaces of the wing or fuselage of the drone 102 (or other aircraft)and/or the payload 104.

After contemplating the disclosure, one skilled in the art appreciatesthat various types of securing means may be used to secure the covermember 902 to the top of the vacuum control unit 206 without departingfrom the novel features of the present invention. Similarly, one skilledin the art appreciates that various types of securing means may be usedto secure the cover member 902 to any type of secured-to object withoutdeparting from the novel features of the present invention. All suchembodiments are intended to be within the scope of this disclosure andto be protected by the accompanying claims.

FIG. 10 is a side cut away view of the vacuum mounting module 1002 withtwo opposing vacuum cups 204. The components and operational features ofthe vacuum mounting module 1002 may the similar to, or the same as, thecomponent and operational features of the vacuum mounting module 202.For brevity, like components and/or operational features are not againdescribed herein for brevity. A practical application of this vacuummounting module 1004 I illustrated in FIG. 6 .

The example embodiment illustrated in FIG. 10 shows two vacuum pumps 804a that establish and maintain a vacuum in their respective vacuum cups204. Alternative embodiments may employ any suitable number and/or typeof vacuum pumps 804.

FIG. 11 is a block diagram of a vacuum mounting module control system1102 employing a designated vacuum control device 208 that controls aplurality of vacuum mounting modules 202. Each of the vacuum mountingmodules 202 (slave device) are controllably coupled to the vacuumcontrol device 208 (master device). Preferably, a master/slave controlsystem enables the vacuum control device 208 to generate and transmitvacuum cup actuation signals and vacuum cup release signals to theplurality of vacuum mounting modules 202 using a suitable near field orwire based communication signal. In some embodiments, a selected one ofthe vacuum mounting modules 202 is designated as the vacuum controldevice 208.

Also, the vacuum control device 208 is configured to receive informationfrom the plurality of vacuum mounting modules 202. Operational statusinformation may be communicated to the vacuum control device 208. Forexample, if one of the vacuum mounting modules 202 fails or begins toloos vacuum pressure, the vacuum control unit 206 can be notified of thefailure and/or loss of vacuum pressure by that particular vacuummounting module 202. Optionally, the vacuum control device 208 mayincrease vacuum pressure within the remaining vacuum mounting modules202 to compensate for the failing vacuum mounting module 202. As anothernon-limiting example, vacuum pressure in one or more of the vacuummounting modules 202 may be selectively modified by the vacuum controldevice 208.

Optionally, the vacuum control device 208 may be communicatively coupledto a remote control and command center 1104. The control and commandcenter 1104 may communicate with the vacuum control device 208 using asuitable wireless communication signal 1106 format, such as a satellitesignal, a cellular communication signal, or the like. The vacuum controldevice 208 can generate and transmit the vacuum cup actuation signalsand the vacuum cup release signals in response to receiving instructionsfrom the control and command center 1104 that is being controlled by thedrone operator. Additionally, or alternatively, the vacuum controldevice 208 may communicate operational status information and/or vacuumpressure information to the control and command center 1104.Accordingly, the drone operator may appreciate the operating conditionof the payload attachment system 100. If the control and command center1104 is a smart phone or the like, an app may be installed on the smartphone that facilitates communications between the smart phone and thevacuum control device 208.

FIG. 12 is a block diagram of a vacuum mounting module control system1202 employing mesh network 704 wherein a plurality of vacuum mountingmodules 202 cooperatively control operation of the payload attachmentsystem 100. Here, individual vacuum mounting modules 202 arecommunicatively coupled together. Each of the vacuum mounting modules202 communicate information to each of the other vacuum mounting modules202, such as operational status and/or vacuum pressure. Accordingly, thevacuum mounting modules 202 cooperatively work together to secure anobject of interest. Some embodiments may employ an artificialintelligence algorithm to more effectively control operation of thepayload attachment system 100.

Optionally, one or more of the vacuum mounting modules 202 may becommunicatively coupled to a control and command center 1104 using asuitable wireless communication signal 1106 format, such as a satellitesignal, a cellular communication signal, or the like. When one or moreof the vacuum mounting modules 202 receives an instruction from theremote control and command center 1104, the receiving vacuum mountingmodule 202 communicates the vacuum cup actuation signal or the vacuumcup release signal to the other vacuum mounting modules 202. In someembodiments, a wire-based communication format may be used.Additionally, or alternatively, the one or more of the vacuum mountingmodules 202 may communicate operational status information and/or vacuumpressure information to the control and command center 1104.Accordingly, the drone operator may appreciate the operating conditionof the payload attachment system 100. If the remote control and commandcenter 1104 is a smart phone or the like, an app may be installed on thesmart phone controlled by the drone operator that facilitatescommunications between the smart phone and the vacuum control device208.

After contemplation of this disclosure, one skilled in the artappreciates that the vacuum mounting modules 202 may be implementedusing any suitable Internet of Things (IOT) technology. All such IOTembodiments, now known or later developed, are intended to be within thescope of this disclosure and to be protected by the accompanying claims.

It should be emphasized that the above-described embodiments of thepayload attachment system 100 are merely possible examples ofimplementations of the invention. Many variations and modifications maybe made to the above-described embodiments. All such modifications andvariations are intended to be included herein within the scope of thisdisclosure and protected by the following claims.

Furthermore, the disclosure above encompasses multiple distinctinventions with independent utility. While each of these inventions hasbeen disclosed in a particular form, the specific embodiments disclosedand illustrated above are not to be considered in a limiting sense asnumerous variations are possible. The subject matter of the inventionsincludes all novel and non-obvious combinations and subcombinations ofthe various elements, features, functions and/or properties disclosedabove and inherent to those skilled in the art pertaining to suchinventions. Where the disclosure or subsequently filed claims recite “a”element, “a first” element, or any such equivalent term, the disclosureor claims should be understood to incorporate one or more such elements,neither requiring nor excluding two or more such elements.

Applicant(s) reserves the right to submit claims directed tocombinations and subcombinations of the disclosed inventions that arebelieved to be novel and non-obvious. Inventions embodied in othercombinations and subcombinations of features, functions, elements and/orproperties may be claimed through amendment of those claims orpresentation of new claims in the present application or in a relatedapplication. Such amended or new claims, whether they are directed tothe same invention or a different invention and whether they aredifferent, broader, narrower, or equal in scope to the original claims,are to be considered within the subject matter of the inventionsdescribed herein.

Therefore, having thus described the invention, at least the followingis claimed:
 1. A payload attachment system that employs at least onevacuum mounting module, the vacuum mounting module comprising: a covermember with an outer surface that is securable to a surface of a wing ora fuselage of a drone; a body member defined by a cavity that is coveredby the cover member during use of the vacuum object mounting system; avacuum cup coupled to the body member, wherein the vacuum cup isdisposed on an exterior of the body member on a side of the body memberopposing the cover member: a microcontroller residing within the cavityof the body member; a vacuum pump residing within the cavity of the bodymember, wherein the vacuum pump is controllably coupled to themicrocontroller, and wherein the vacuum pump is fluidly coupled to thevacuum cup; and a power source controllably coupled to themicrocontroller and connected to the vacuum pump, wherein the powersource powers the vacuum pump in response to an actuation signalreceived at the microcontroller to cause the vacuum pump to create apredefined vacuum pressure between a surface of a payload and the vacuumcup, wherein the vacuum mounting module further comprises: a vacuumchamber in fluid communication with the vacuum pump and the vacuum cup;and a check valve disposed between the vacuum chamber and the vacuumcup, wherein the microcontroller actuates the vacuum pump to maintainthe predefined vacuum pressure in the vacuum chamber, and wherein thecheck valve has a cracking pressure corresponding to the predefinedvacuum pressure such that the predefined vacuum pressure is maintainedwithin the vacuum cup when the vacuum cup mounting system is secured tothe surface of the payload.
 2. A payload attachment system that employsat least one vacuum mounting module, the vacuum mounting modulecomprising: a cover member with an outer surface that is securable to asurface of a wing or a fuselage of a drone; a body member defined by acavity that is covered by the cover member during use of the vacuumobject mounting system; a vacuum cup coupled to the body member, whereinthe vacuum cup is disposed on an exterior of the body member on a sideof the body member opposing the cover member: a microcontroller residingwithin the cavity of the body member; a vacuum pump residing within thecavity of the body member, wherein the vacuum pump is controllablycoupled to the microcontroller, and wherein the vacuum pump is fluidlycoupled to the vacuum cup; and a power source controllably coupled tothe microcontroller and connected to the vacuum pump, wherein the powersource powers the vacuum pump in response to an actuation signalreceived at the microcontroller to cause the vacuum pump to create apredefined vacuum pressure between a surface of a payload and the vacuumcup, wherein the vacuum mounting module further comprises: a manualactuator disposed on an outer surface of the vacuum cup mounting systemand communicatively coupled to the microcontroller, wherein a payloadinstaller actuates the manual actuator to release the vacuum cupmounting system from the surface of the payload, wherein the manualactuator communicates a release signal to the microcontroller inresponse to actuation by the payload installer, and wherein themicrocontroller actuates the vacuum pump to release the vacuum cupmounting system from the surface of the payload in response to receivingthe release signal, wherein a payload installer further actuates themanual actuator to secure the vacuum cup mounting system to the surfaceof the payload, wherein the manual actuator communicates the actuationsignal to the microcontroller in response to further actuation by thepayload installer, and wherein the microcontroller actuates the vacuumpump to secure the vacuum cup mounting system to the surface of thepayload in response to receiving the actuation signal.
 3. A payloadattachment system that employs at least one vacuum mounting module, thevacuum mounting module comprising: a cover member with an outer surfacethat is securable to a surface of a wing or a fuselage of a drone; abody member defined by a cavity that is covered by the cover memberduring use of the vacuum object mounting system; a vacuum cup coupled tothe body member, wherein the vacuum cup is disposed on an exterior ofthe body member on a side of the body member opposing the cover member;a microcontroller residing within the cavity of the body member; avacuum pump residing within the cavity of the body member, wherein thevacuum pump is controllably coupled to the microcontroller, and whereinthe vacuum pump is fluidly coupled to the vacuum cup; and a power sourcecontrollably coupled to the microcontroller and connected to the vacuumpump, wherein the power source powers the vacuum pump in response to anactuation signal received at the microcontroller to cause the vacuumpump to create a predefined vacuum pressure between a surface of apayload and the vacuum cup, wherein the vacuum mounting module furthercomprises: an indicator light disposed on an outer surface of the vacuumcup mounting system and communicatively coupled to the microcontroller,wherein the microcontroller actuates the indicator light in response tosecuring the vacuum cup mounting system to the surface of the payload,wherein the indicator light illuminates in response to securing thevacuum cup unit to the surface of the payload, and wherein a payloadinstaller may view the indicator light to intuitively understand whetherthe vacuum cup mounting system is secured to the surface of the payload.4. A payload attachment system that employs at least one vacuum mountingmodule, the vacuum mounting module comprising: a cover member with anouter surface that is securable to a surface of a wing or a fuselage ofa drone; a body member defined by a cavity that is covered by the covermember during use of the vacuum object mounting system; a vacuum cupcoupled to the body member, wherein the vacuum cup is disposed on anexterior of the body member on a side of the body member opposing thecover member: a microcontroller residing within the cavity of the bodymember; a vacuum pump residing within the cavity of the body member,wherein the vacuum pump is controllably coupled to the microcontroller,and wherein the vacuum pump is fluidly coupled to the vacuum cup; and apower source controllably coupled to the microcontroller and connectedto the vacuum pump, wherein the power source powers the vacuum pump inresponse to an actuation signal received at the microcontroller to causethe vacuum pump to create a predefined vacuum pressure between a surfaceof a payload and the vacuum cup, wherein the vacuum cup mounting systemis one of a plurality of vacuum cup mounting systems, and wherein eachone of the plurality of vacuum cup mounting systems further comprise: atransceiver communicatively coupled to the respective microcontroller,wherein each one of the microcontrollers of the plurality vacuum cupmounting systems are in communication with a vacuum control device, andwherein each of the vacuum pumps of the plurality of vacuum cup mountingsystems operate to create the vacuum between the surface of the payloadand the vacuum cup in response to their respective microcontrollerreceiving the actuation signal from the vacuum control device via therespective transceiver.
 5. A payload attachment system that employs atleast one vacuum mounting module, the vacuum mounting module comprising:a cover member with an outer surface that is securable to a surface of awing or a fuselage of a drone; a body member defined by a cavity that iscovered by the cover member during use of the vacuum object mountingsystem; a vacuum cup coupled to the body member, wherein the vacuum cupis disposed on an exterior of the body member on a side of the bodymember opposing the cover member: a microcontroller residing within thecavity of the body member; a vacuum pump residing within the cavity ofthe body member, wherein the vacuum pump is controllably coupled to themicrocontroller, and wherein the vacuum pump is fluidly coupled to thevacuum cup: a power source controllably coupled to the microcontrollerand connected to the vacuum pump; and an outer seal, wherein the outerseal corresponds to a shape and size of a selected portion of thepayload, wherein a plurality of vacuum mounting modules are configuredto cooperatively secure payload to the drone, and wherein the powersource powers the vacuum pump in response to an actuation signalreceived at the microcontroller to cause the vacuum pump to create apredefined vacuum pressure between a surface of a payload and the vacuumcup.
 6. The payload attachment system of claim 5, wherein the outer sealfurther comprises: one of a ferromagnetic strip or an electromagneticstrip, wherein the ferromagnetic strip or the electromagnetic strip areconfigured to hold the outer seal in a selected location on one of thedrone or the payload while a payload installer is securing the payloadto the drone.
 7. A payload attachment system that employs at least onevacuum mounting module, the vacuum mounting module comprising: a covermember with an outer surface that is securable to a surface of a wing ora fuselage of a drone; a body member defined by a cavity that is coveredby the cover member during use of the vacuum object mounting system; avacuum cup coupled to the body member, wherein the vacuum cup isdisposed on an exterior of the body member on a side of the body memberopposing the cover member: a microcontroller residing within the cavityof the body member; a vacuum pump residing within the cavity of the bodymember, wherein the vacuum pump is controllably coupled to themicrocontroller, and wherein the vacuum pump is fluidly coupled to thevacuum cup; and a power source controllably coupled to themicrocontroller and connected to the vacuum pump, wherein the powersource powers the vacuum pump in response to an actuation signalreceived at the microcontroller to cause the vacuum pump to create apredefined vacuum pressure between a surface of a payload and the vacuumcup, wherein the vacuum mounting module further comprises: at least oneenvironmental sensor communicatively coupled to the transceiver and thatsenses an environmental condition, wherein the at least oneenvironmental sensor communicates environmental informationcorresponding to the sensed environmental condition to the transceiver,wherein the received environmental information is communicated from thetransceiver to the vacuum control device, and wherein the vacuum controldevice determines an adjustment to the predefined vacuum pressure basedon the received environmental information.
 8. A payload attachmentsystem that employs at least one vacuum mounting module, the vacuummounting module comprising: a cover member with an outer surface that issecurable to a surface of a wing or a fuselage of a drone; a body memberdefined by a cavity that is covered by the cover member during use ofthe vacuum object mounting system; a vacuum cup coupled to the bodymember, wherein the vacuum cup is disposed on an exterior of the bodymember on a side of the body member opposing the cover member: amicrocontroller residing within the cavity of the body member; a vacuumpump residing within the cavity of the body member, wherein the vacuumpump is controllably coupled to the microcontroller, and wherein thevacuum pump is fluidly coupled to the vacuum cup; and a power sourcecontrollably coupled to the microcontroller and connected to the vacuumpump, wherein the power source powers the vacuum pump in response to anactuation signal received at the microcontroller to cause the vacuumpump to create a predefined vacuum pressure between a surface of apayload and the vacuum cup, wherein a plurality of vacuum mountingmodules further comprises: a transceiver, wherein the correspondingmicrocontroller communicates adjustment information corresponding to theadjustment to the predefined vacuum pressure to the correspondingtransceiver, wherein the corresponding transceiver broadcasts theadjustment information, wherein the transceivers in the other pluralityof vacuum cup units receive the broadcasted adjustment information, andwherein the corresponding microcontrollers effect the adjustment totheir predefined vacuum pressure based on the received adjustmentinformation.
 9. A payload attachment system that employs at least onevacuum mounting module, the vacuum mounting module comprising: a covermember with an outer surface that is securable to a payload; a bodymember defined by a cavity that is covered by the cover member duringuse of the vacuum object mounting system; a vacuum cup coupled to thebody member, wherein the vacuum cup is disposed on an exterior of thebody member on a side of the body member opposing the cover member: amicrocontroller residing within the cavity of the body member; a vacuumpump residing within the cavity of the body member, wherein the vacuumpump is controllably coupled to the microcontroller, and wherein thevacuum pump is fluidly coupled to the vacuum cup; and a power sourcecontrollably coupled to the microcontroller and connected to the vacuumpump, wherein the power source powers the vacuum pump in response to anactuation signal received at the microcontroller to cause the vacuumpump to create a predefined vacuum pressure between a surface of a wingor a fuselage of a drone and the vacuum cup, wherein the cover membercomprises: an attachment means configured to attach the outer surface ofthe cover member to the drone.
 10. A payload attachment system thatemploys at least one vacuum mounting module, the vacuum mounting modulecomprising: a cover member with an outer surface that is securable to apayload; a body member defined by a cavity that is covered by the covermember during use of the vacuum object mounting system; a vacuum cupcoupled to the body member, wherein the vacuum cup is disposed on anexterior of the body member on a side of the body member opposing thecover member: a microcontroller residing within the cavity of the bodymember; a vacuum pump residing within the cavity of the body member,wherein the vacuum pump is controllably coupled to the microcontroller,and wherein the vacuum pump is fluidly coupled to the vacuum cup; and apower source controllably coupled to the microcontroller and connectedto the vacuum pump, wherein the power source powers the vacuum pump inresponse to an actuation signal received at the microcontroller to causethe vacuum pump to create a predefined vacuum pressure between a surfaceof a wing or a fuselage of a drone and the vacuum cup, and wherein theattachment means is configured to releasably attach the outer surface ofthe cover member to the drone.
 11. A payload attachment system thatemploys at least one vacuum mounting module, the vacuum mounting modulecomprising: a cover member with an outer surface that is securable to apayload; a body member defined by a cavity that is covered by the covermember during use of the vacuum object mounting system; a vacuum cupcoupled to the body member, wherein the vacuum cup is disposed on anexterior of the body member on a side of the body member opposing thecover member: a microcontroller residing within the cavity of the bodymember; a vacuum pump residing within the cavity of the body member,wherein the vacuum pump is controllably coupled to the microcontroller,and wherein the vacuum pump is fluidly coupled to the vacuum cup: apower source controllably coupled to the microcontroller and connectedto the vacuum pump; and an outer seal, wherein the outer sealcorresponds to a shape and size of a selected portion of the payload,wherein the power source powers the vacuum pump in response to anactuation signal received at the microcontroller to cause the vacuumpump to create a predefined vacuum pressure between a surface of a wingor a fuselage of a drone and the vacuum cup, wherein a plurality ofvacuum mounting modules are configured to cooperatively secure payloadto the drone.
 12. The payload attachment system of claim 11, wherein theouter seal further comprises: one of a ferromagnetic strip or anelectromagnetic strip, wherein the ferromagnetic strip or anelectromagnetic strip are configured to hold the outer seal in aselected location on one of the drone or the payload while a payloadinstaller is securing the payload to the drone.
 13. A payload attachmentsystem that employs at least one vacuum mounting module, the vacuummounting module comprising: a cover member with an outer surface that issecurable to a payload; a body member defined by a cavity that iscovered by the cover member during use of the vacuum object mountingsystem; a first vacuum cup coupled to the body member, wherein thevacuum cup is disposed on an exterior of the body member; a secondvacuum cup coupled to the body member, wherein the vacuum cup isdisposed on an exterior of the body member on a side of the body memberopposing the first vacuum cup; a microcontroller residing within thecavity of the body member; a first vacuum pump residing within thecavity of the body member, wherein the first vacuum pump is controllablycoupled to the microcontroller, and wherein the first vacuum pump isfluidly coupled to the first vacuum cup; a second vacuum pump residingwithin the cavity of the body member, wherein the second vacuum pump iscontrollably coupled to the microcontroller, and wherein the secondvacuum pump is fluidly coupled to the second vacuum cup; and a powersource controllably coupled to the microcontroller and connected to thefirst vacuum pump and the second vacuum pump, wherein the power sourcepowers the first vacuum pump in response to a first actuation signalreceived at the microcontroller to cause the first vacuum pump to createa predefined vacuum pressure between a surface of a wing or a fuselageof a drone and the first vacuum cup, and wherein the power source powersthe second vacuum pump in response to a second actuation signal receivedat the microcontroller to cause the second vacuum pump to create apredefined vacuum pressure between a surface of the payload and thesecond vacuum cup.